Method for separation of a fluid monergol for running a rocket motor

ABSTRACT

A method for the separation of a fluid Monergol in order to run a gas generator especially for rocket motors comprises dividing the fluid Monergol mass into a plurality of separate Monergol partial masses, separating one of the masses catalytically in an atomized state, and mixing another of the monergol partial masses in an atomized state with the hot decomposed gases of the first Monergol partial mass which is generated as it is separated catalytically so as to thermally split the second fluid Monergol partial mass.

United States Patent [191 Munding [451 Nov. 20, 1973 METHOD FORSEPARATION OF A FLUID MONERGOL FOR RUNNlNG A ROCKET MOTOR [75] Inventor:German Munding, Bad

Friedrichshall, Germany [73] Assignee: Bolkow Gesellschaft mitbeschrankter Haftung, Ottobrum bei Munich, Germany [22] Filed: July 2,11970 [21] Appl. No.: 60,967

Related U.S. Application Data [62] Division of Ser. No. 767,906, Sept.23, 1968, Pat.

10/1953 Carr 60/207 X 2,648,317 8/1953 Mikulasek 149/36 3,230,701 1/19663,173,247 3/1965 2,930,184 3/1960 Plescia 60/218 PrimaryExaminer-Benjamin R. Padgett Attorney-McGlew & Toren [5 7 ABSTRACT Amethod for the separation of a fluid Monergol in order to run a gasgenerator especially for rocket m0- tors comprises dividing the fluidMonergol mass into a plurality of separate Monergol partial masses,separating one of the masses catalytically in an atomized state, andmixing another of the monergol partial masses in an atomized state withthe hot decomposed gases of the first Monergol partial mass which isgenerated as it is separated catalytically so as to thermally split thesecond fluid Monergol partial mass.

8 Claims, 4 Drawing Figures Flg3 lNVENTOR Gennan Mundmg ATTORNEYS METHODFOR SEPARATHUN (NF A FLUID MONERGOL lFQlR RUNNING A ROCKET MOTOR This isa division of application Ser. No. 767,906, filed Sept. 23, 1968, nowU.S. Pat. No. 3,600,861.

An apparatus for carrying out the method of the invention, in oneembodiment, includes a housing defining a first injection chamber forinjecting a first partial Monergol mass and which is connected to acatalyzator chamber for flow of the atomized liquid mass therethrough,and a second injection chamber located downstream of the catalyzerchamber into which a second partial Monergol mass is directed into theflow stream of the first catalyzed mass. The construction is such thatthe flow through the catalyzer is in an axial direction and transverselyinto the injected stream of the second partial mass for return axialflow and entrance into a thrust nozzle for discharge in a reversedirection. The injection nozzle is advantageously arranged in a ringhaving vanes for producing the tangential whirling flow of the injectedpartial Monergol mass.

In another embodiment of the invention, a gas generator housing,includes a double wall closed end with a first injection nozzle arrangedtoddischarge a first fluid Monergol mass into the inner wallmcharnberfor flow in an axial direction through the catalyzer arranged as a partof an intermediate ring sector within the housing. The flow of the firstmass from the catalyzer is then around a peripheral ring portion betweenthe double walls of the housing and into another ring sector into whicha second partial mass is injected. The third partial Monergol mass isadded between the wall portions and is directed with the combined firstand second partial mass portions in the ring sectors, and flow from thering sectors is tangentially inwardly to a centrally arranged swirlchamber which opens downwardly or inwardly into a thrust nozzle throughwhich the products are discharged.

SUMMARY OF THE INVENTION This invention relates, in general, to a methodand apparatus for generating gases from a fluid Monergol and, inparticular, to a new and useful method and apparatus for generatinggases from a fluid Monergol, particularly for running a gas generatorsuch as a rocket motor.

Gas generators especially for rocket motors employing catalyticseparation of a fluid Monergol are known. In the known gas generators,the fluid Monergol mass is sent in an atomized state through a catalyticreactor and is separated into separate gases under high heat conditions.In addition to the basic advantages afforded by catalytically operatedgenerators they have the disadvantage that the catalytic equipment toseparate the Monergols requires a large amount of space in order tosatisfactorily fulfill its requirements. This is particularly importantin respect to the construction of rocket engines particularly for airand space travel. In addition, the catalyzator must be made of expensivemetals and therefore the equipment is very expensive to manufacture.

In accordance with the present invention, there is provided a highproduction gas generator for a simple construction and relativelyinexpensive and it may be made to a very small size. This is madepossible in accordance with the method of the invention by separating afluid Monergol gas mass into at least two Monergol parts. One of theMonergol parts is separated catalytically in an atomized state. Anotherof the fluid partial Monergol masses is mixed in an atomized state intothe hot separated gases of the first partial Monergol mass and istherefore split by it thermically. A predetermined ratio is chosenbetween the two Monergol masses based on the consideration that thecatalytically separated Monergol mass must be of a large enoughproportion so that the heat capacity of the separated gas is sufficientto separate the second partial Monergol mass by thermal reaction.

In a refinement of the invention, it is also proposed that during thesplitting of the fluid Monergol mass into more than two partial fluidMonergol parts in which the firstpartial Monergol mass which is producedcatalytically in an atomized state and which is brought into contactwith the second partial Monergol mass of a greater volume and which isalso in an atomized state, a further fluid Monergol mass is added in theatomized state to the hot cracked gases of the previous two and also ina correspondingly increasing amount so that it is thermically separatedby the cracked gases of the previous Monergol masses and so on. In orderto achieve an absolute control over the complete separation of the firstand second partial Monergol masses, they are directed in the specificatomized amounts contained in the cracked gas through a so-calledspecial safety catalyzator.

An additional feature of the invention method and apparatus is that itpermits the previously cracked partial Monergol masses to be broughtinto engagement with a newly introduced partial Monergol mass in theform of a tangential whirling stream. For this purpose, an apparatuscomprises, for example, a gas generating chamber housing having anexterior chamber into which the first Monergol mass is introduced. it isarranged so that it will flow through an annular catalyzer chamber andin an axial direction and then transversely through a ring member havingtangential blades so that it is whirled into association with a secondpartial Monergol mass which is introduced at this location. Both gaseousproducts have been directed in an opposite axial direction and arereversed for flow and discharge out through a nozzle section in the formof thrust gases. Each successive partial Monergol mass is introduced bya nozzle providing for the atomization of the partial Monergol mass.

In accordance with another embodiment of the invention, the gasgenerator includes an annular catalytic ring sector arranged at alocation spaced from the inner wall of a reactor of generator housing.The ring sector is divided up into a plurality of individual partialsectors. A first Monergolic mass is introduced, for example, in a mannersuch that it will flow through one of the catalytic ring sector portionsand thence outwardly through this sector portion after some axial flowfor contact by a second Monergolic partial mass which is introduced byan injector disposed in a chamber around the catalytic ring. Thecombined gases of the first and second partial Monergol masses are thendirected into a partial ring sector which is referred to a safetycatalyzator. The combined products are moved in a whirling direction anda further third Monergolic partial mass is added prior to a third passthrough a sector portion of the catalyst mass. The resultant productsare directed tangentially into a central whirling chamber which opens atone end to a chamber having a thrust nozzle discharge.

Accordingly, it is an object of the invention to provide a method forthe separation of a fluid Monergol to run a gas generator, especiallyfor rocket motors comprising dividing a fluid Monergol mass into atleast two separate Monergol partial masses, separating one of saidpartial masses catalytically while in an atomized state, directing asecond fluid Monergol partial mass in an atomized state into the hotdecomposed gases of the first partial Monergol mass so as to beintermixed therewith and thermally split by it.

A further object of the invention is to provide an apparatus forgenerating gas which comprises a housing having a closed end with meansfor introducing a first Monergolic mass into an injection chamber in anatomized state, the injection chamber being connected to a catalystchamber through which the first partial Monergol mass is directed, meansfor introducing a second partial Monergol mass into the hot gasesgenerated in the catalyst chamber by the first partial Monergol mass,and a thrust nozzle arranged to receive the combined gases and fordischarging them outwardly.

A further object of the invention is to provide a generator whichincludes a plurality of separate catalyst chambers with means forsuccessively introducing partial Monergol masses such that each insuccession flows through a partial chamber and is then removed passedthe injection means for another, with means for tangentially moving thehot gases which are generated so that they intermix with the nextinjection of the Monergol mass so that the hot decomposed gases cause aspliting of the newly introduced mass, and including one or more meansfor adding additional partial Monergol masses and for directing thecombined decomposed gases through a whirling chamber for directing thegases outwardly through a thrust nozzle.

A further object of the invention is to provide an apparatus forgenerating gases which is simple in design, rugged in construction andeconomical to manufacture.

The various features of novelty which characterize the invention arepointed out with particularity in the claims annexed to and forming apart of this specification. For a better understanding of the invention,its operating advantages and specific objects attained by its use,reference should be had to the accompanying drawings and descriptivematter in which there are illustrated and described preferredembodiments of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS In the Drawings:

FIG. 1 is a transverse sectional view of a gas generator for a rocketmotor constructed in accordance with the invention;

FIG. 2 is a section taken on the line IIII of FIG. 1;

FIG. 3 is a view similar to FIG. 1 of another embodiment of theinvention; and

FIG. 4 is a section taken on the line IV-IV of FIG. 3.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Referring to thedrawings, in particular, the invention embodied therein in FIG. 1,comprises a gas generator housing and rocket engine generally designated50 having spaced inner and outer walls 52 and 54 and a central nozzleforming member 8. The nozzle has an opened discharge end 8a, but thewalls 52 and 54 or continuations thereof substantially close theremaining portion of the gas generator rocket engine 50.

In accordance with the invention, an injection chamber 1 is provided fora first Monergol mass in a location adjacent the end remote from thenozzle discharge 8a. Into the space 1, the first Monergol mass isdirected by the discharge from injection nozzles 2 in an atomized state.

The chamber 1 communicates to an annular passage having a catalyst or acatalyzator passages 3. The atomized Monergol mass 9 flows through thecatalyzator 3 and is separated into individual gases and under highheating conditions cracked gases 9a are created.

A nozzle ring 4 is located adjacent the discharge end 8a of the nozzleat a location around the nozzle walls and in a position to receive thegases 9a to permit them to be directed as indicated by the arrow in FIG.2 tangentially into an annular chamber 56 located at the lower end ofthe housing 50 as indicated in FIG. 1. A second partial Monergol mass isintroduced through a feed line 6 and an injection nozzle 7 into theannular chamber 56in the stream of gases 9a. The hot gases 9a which areaccelerated by the nozzle ring 4 contact the second partial Monergolmass 10 and are mixed with it into the tangential movement thereof. Thetwo gaseous mediums produced, 9a and 10a, move tangentially upwardlyaround the nozzle wall 8 as indicated by the arrows in FIG. 1. The spacebetween the nozzle 8 and the wall 52 defines a cyclone chamber 5. Theatomized second Monergol mass 10 is added at a location within theconfines of the periphery of this whirling stream until the addedMonergol mass is thermically separated. Adjacent' the concial endportion of the wall 52 the combined gases reverse and flow outwardlythrough the thrust nozzle 8 and are discharged through the opening 8a.

In the embodiment indicated in FIGS. 3 and 4, there is provided a gasgenerator rocket engine generally 50. This generator 50' also includesspaced inner and outer walls 52' and 54. In this embodiment, acatalyzator 3' is located on the interior of the inner wall 52 and it isadvantageously divided up into a plurality of individual segments orcompartments by radial walls 58. A first injector chamber 11 is definedbetween an end portion of the inner wall 52' and an end wall 60 of thecatalyzator 3. A first injection nozzle 12 is provided for injecting afirst partial Monergol mass into the injection chamber 11 whichcommunicates with a ring sector 13 of the catalyzator 3'.

Full radial walls 58' divide the section between the interior walls 52'and 54 into four annular sectors including a second mixing chamberportion 14 into which a second injector nozzle 15 directs a secondpartial Monergol mass. The flow of the gases from the second mixingchamber 14 is through a second catalyzator 16 and into a cyclone 17arranged centrally within the catalyzator 3. Swirl impellers 22 arelocated between the various sectors to impart a swirl to the gases asthey enter the cyclone 17. A third injection nozzle 18 is lo cated todischarge a third partial Monergol mass in an axial direction into thecylcone 17. A thurst nozzle 19 connects to the lower End of the cyclonel7 and is provided with an opening 19a for the discharge of the thrustgases.

The atomized Monergol mass 20 which is introduced to the first injectionchamber 1 1 flows through the catalyzator ring section 13 in an axialdirection to the opposite end which is closed by a wall 62. During thisflow, it is separated into individual mass and under the high heatconditions cracked gases 20a are created. The cracked gases 20a leave ina radial direction from the ring section 13 and enter into the secondinjection or mixing chamber 14. A second atomized Monergol partial mass21 is directed into and admixed with the hot cracked gases 20a and isseparated thermically by the heat of these gases to form the hot crackedgases 21a.

Both the gases 20a and 21a then flow through the catalyzator ringsection 16 which eventually separates the Monergol particles which arestill in fluid form. The swirl impellers 22 impart a swirl to the gases20a and 21a which flow into the cyclone 17. Into this swirl stream, athird Monergol partial mass 23 is injected by the nozzle 18 and it isseparated by the heat of the gases 20a and 21a. The thrust nozzle 19 isfed by the aerodynamic and thermal-dynamic conditions inside the chamber22 fromthecenter of the swirling stream; remaining Monergol drops 23 arekept within the confines of the periphery of the swirl stream until theyare thermically separated. V M

If, as Monergol hydrazine is used, then the mixing ratio of the firstand second Monergol masses 9 and is maintained about 1:2 for theembodiments of FIGS. 1 and 2. This means, that only about a third of theentire Monergol mass is fed through the catalyzator 3. Therefore, thiscatalyzator 3 can be of a considerably smaller dimension than the usualgas generator elements. The heat of the gases of the first Monergolpartial mass 9 consisting of only a third of the entire Monergol mass issufficient to separate thermically the remaining two thirds of thepartial Monergol mass which is introduced at the second injection.

In the embodiment according to FIGS. 3 and 4, if a hydrazine is alsoused, only about 11 percent of the entire Monergol mass is sufficientfor the first Monergol partial mass injection at the location of theinjector 20. A correspondingly smaller sized catalyzator ring sector 3is therefore required. The second Monergol partial mass 21 can amount toa maximum of about 22 percent of the entire Monergol mass in order topermit it to split by the gases 20a of the first Monergol partial mass20. The gases 20a and 21a of the Monergol masses 20 and 21 arethemselves capable of thermically separating the remaining 67 percentwhich is introduced in the form of a third Monergol partial mass 23.

The second catalyzator ring sector 116 performs a safety purposeinasmuch as they are intended to guarantee a complete separation of theMonergol masses 20 and 211 of the first and second Monergol partialinjections 20 and 21 under maximum conditions which are to be theoptimum of the installation to be obtained. It is possible, in theory,to keep the first catalyzator very small and to create all followingprocesses purely thermically in the form of cascading admixtures of manypartial Monergol masses. Practical considerations put a limit on thenumber of steps of injections. it lies entirely within the limits of thepresent invention that instead of a first Monergol partial mass such asthe mass 10 or the mass 20 and which are chemically similar to thesecond and/or third Monergol masses 11 and 21 or 23, to use instead onewhich comprises the first Monergol mass 10 or 20 and then to add achemically different second and/or third Monergol mass.

What is claims is:

1. A method for running a gas generator, especially for running rocketmotors, comprising individually dividing a fluid Monergol mass into atleast two separate Monergol partial masses, directing the first Monergolpartial mass into association with a catalyst to catalyti cally separatethe first fluid Monergol partial mass in an atomized state to form hotdecomposed gases, moving the decomposed gases in a whirling flow arounda central area of the gas generator, and mixing the other fluid Monergolpartial mass by directing it into the whirling hot decomposed gases ofthe first Monergol partial mass so as to thermically split the otheradded Monergol partial mass.

2. A method, according to claim 1, wherein the entire Monergol mass issplit into more than two fluid Monergol partial masses and wherein afterthe first Monergol partial mass is separated catalytically in anatomized state a second larger volume Monergol partial mass is added inthe atomized state to the catalytically created decomposed gases of thefirst partial Monergol mass and it is split thermically thereby, and thenext fluid Monergol partial mass is mixed in an atomized state to thehot gases produced by each of the first and second Monergol partialmasses.

3. A method, according to claim 2, wherein the first and second Monergolpartial masses after they are catalytically separated to form decomposedgases are again subjected to catalytic separation to insure that all ofthe atomized Monergol particles are decomposed.

4. A method, according to claim 1, wherein decomposed masses and thepartial Monergol mass which is added to the decomposed gases are whirledtogether when admixed.

5, A method of operating a rocket engine using a combustion chamberhaving a catalyst therein, comprising discharging a first portion of apropellant component in a spray into the combustion chamber anddirecting the spray in a flow into association with the catalyst togenerate high temperature gases and to create cracked gases moving thegases in a whirling flow around the central portion of the combustionchamber, and directing a second portion of a propellant component intomixing association with the whirling cracked gases in the samecombustion chamber downstream of the introduction of the first portionto subject them to the high temperatures of the cracked gases and tothermally separate the second portion of said propellant component, anddischarging the combined gases which are formed.

6. A method of operating a rocket engine using a combustion chamberhaving a catalyst therein, comprising discharging a first portion of apropellant component in a spray into the combustion chamber anddirecting the spray in a flow into association with the catalyst togenerate high temperature gases and to create cracked gases, anddirecting a second portion of a propellant component into mixingassociation with the cracked gases in the same combustion chamberdownstream of the introduction of the first portion to subject tion withthe catalyst and then is directed in a whirling inward flow within thecombustion chamber, and directing the second portion of the propellantcomponent into the whirling inward flow of the cracked gases.

7. A method of operating a rocket engine, according to claim 6,including injecting a third portion of the propellant component intoassociation with the catalyst downstream of the first portion and thendirecting the gases after they pass into association with the catalystand are cracked, into a central whirling stream, and introducing saidsecond propellant component into the whirling stream of the crackedgases in the center of the combustion chamber.

8. A method of operating a rocket engine using a combustion chamberhaving a catalyst th'erein, comprising discharging a first portion of apropellant component in a spray into the combustion chamber anddirecting the spray in a flow into association with the catalyst togenerate high temperature gases and to create cracked gases, anddirecting a second portion of a propellant component into mixingassociation with the whirling cracked gases in the same combustionchamber downstream of the introduction of the first portion to subjectthem to the high temperatures of the cracked gases and to thermallyseparate the second portion of said propellant component, anddischarging the combinedgases which are formed, and wherein after thesecond propellant component portion is directed into association withthe cracked gases, the combined gases are directed in an axial directionand are thereafter discharged in a reverse flow axial direction.

1. A method for running a gas generator, especially for running rocketmotors, comprising individually dividing a fluid Monergol mass into atleast two separate Monergol partial masses, directing the first Monergolpartial mass into association with a catalyst to catalytically separatethe first fluid Monergol partial mass in an atomized state to form hotdecomposed gases, moving the decomposed gases in a whirling flow arounda central area of the gas generator, and mixing the other fluid Monergolpartial mass by directing it into the whirling hot decomposed gases ofthe first Monergol partial mass so as to thermically split the otheradded Monergol partial mass.
 2. A method, according to claim 1, whereinthe entire Monergol mass is split into more than two fluid Monergolpartial masses and wherein after the first Monergol partial mass isseparated catalytically in an atomized state a second larger volumeMonergol partial mass is added in the atomized state to thecatalytically created decomposed gases of the first partial Monergolmass and it is split thermically thereby, and the next fluid Monergolpartial mass is mixed in an atomized state to the hot gases produced byeach of the first and second Monergol partial masses.
 3. A method,according to claim 2, wherein the fIrst and second Monergol partialmasses after they are catalytically separated to form decomposed gasesare again subjected to catalytic separation to insure that all of theatomized Monergol particles are decomposed.
 4. A method, according toclaim 1, wherein decomposed masses and the partial Monergol mass whichis added to the decomposed gases are whirled together when admixed.
 5. Amethod of operating a rocket engine using a combustion chamber having acatalyst therein, comprising discharging a first portion of a propellantcomponent in a spray into the combustion chamber and directing the sprayin a flow into association with the catalyst to generate hightemperature gases and to create cracked gases moving the gases in awhirling flow around the central portion of the combustion chamber, anddirecting a second portion of a propellant component into mixingassociation with the whirling cracked gases in the same combustionchamber downstream of the introduction of the first portion to subjectthem to the high temperatures of the cracked gases and to thermallyseparate the second portion of said propellant component, anddischarging the combined gases which are formed.
 6. A method ofoperating a rocket engine using a combustion chamber having a catalysttherein, comprising discharging a first portion of a propellantcomponent in a spray into the combustion chamber and directing the sprayin a flow into association with the catalyst to generate hightemperature gases and to create cracked gases, and directing a secondportion of a propellant component into mixing association with thecracked gases in the same combustion chamber downstream of theintroduction of the first portion to subject them to the hightemperatures of the cracked gases and to thermally separate the secondportion of said propellant component, and discharging the combined gaseswhich are formed; wherein the first portion of the propellant componentis directed outwardly into association with the catalyst and then isdirected in a whirling inward flow within the combustion chamber, anddirecting the second portion of the propellant component into thewhirling inward flow of the cracked gases.
 7. A method of operating arocket engine, according to claim 6, including injecting a third portionof the propellant component into association with the catalystdownstream of the first portion and then directing the gases after theypass into association with the catalyst and are cracked, into a centralwhirling stream, and introducing said second propellant component intothe whirling stream of the cracked gases in the center of the combustionchamber.
 8. A method of operating a rocket engine using a combustionchamber having a catalyst therein, comprising discharging a firstportion of a propellant component in a spray into the combustion chamberand directing the spray in a flow into association with the catalyst togenerate high temperature gases and to create cracked gases, anddirecting a second portion of a propellant component into mixingassociation with the whirling cracked gases in the same combustionchamber downstream of the introduction of the first portion to subjectthem to the high temperatures of the cracked gases and to thermallyseparate the second portion of said propellant component, anddischarging the combined gases which are formed, and wherein after thesecond propellant component portion is directed into association withthe cracked gases, the combined gases are directed in an axial directionand are thereafter discharged in a reverse flow axial direction.